CA2528049A1 - Airfoil platform impingement cooling - Google Patents
Airfoil platform impingement cooling Download PDFInfo
- Publication number
- CA2528049A1 CA2528049A1 CA002528049A CA2528049A CA2528049A1 CA 2528049 A1 CA2528049 A1 CA 2528049A1 CA 002528049 A CA002528049 A CA 002528049A CA 2528049 A CA2528049 A CA 2528049A CA 2528049 A1 CA2528049 A1 CA 2528049A1
- Authority
- CA
- Canada
- Prior art keywords
- platform
- plenum
- airfoil
- turbine
- back side
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000001816 cooling Methods 0.000 title claims abstract 6
- 239000007789 gas Substances 0.000 claims 10
- 239000002826 coolant Substances 0.000 claims 7
- 239000000567 combustion gas Substances 0.000 claims 3
- 238000000034 method Methods 0.000 claims 2
- 238000010926 purge Methods 0.000 claims 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
- F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/80—Platforms for stationary or moving blades
- F05D2240/81—Cooled platforms
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Architecture (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
A gas turbine engine airfoil has a platform cooling scheme including an impingement hole for directing cooling air against an undersurface of the airfoil platform.
Claims (18)
1. An airfoil for a gas turbine engine, the airfoil comprising at least a platform having a gas path side and a back side, an airfoil portion extending from the gas path side of the platform, and a plenum located on a side of the platform opposite said airfoil portion, the plenum communicating with a source of coolant, the plenum having an outlet hole extending through a wall thereof, the outlet hole having an exit facing the back side of the platform and oriented for directing the coolant thereagainst.
2. The airfoil as defined in claim 1, wherein said outlet hole has an axis intersecting the platform.
3. The airfoil as defined in claim 2, wherein said axis is slanted relative to said platform.
4. The airfoil as defined in claim 1, wherein said plenum is defined in a root portion depending from the back side of the platform.
5. The airfoil as defined in claim 5, wherein the wall in which is defined said at least one outlet hole includes a rear mounting flange forming part of the root portion.
6. The airfoil as defined in claim 1, wherein said platform prevents coolant to flow from the plenum to the gas path side of the platform.
7. The airfoil as defined in claim 1, wherein said airfoil includes a turbine vane.
8. A turbine vane for a gas turbine engine, comprising: a platform having a gas path side, a back side opposite said gas path side, and an overhanging portion; an airfoil portion extending from said gas path side of said platform;
a plenum located on the back side of the platform; and at least one impingement hole extending through a wall of the plenum and having an axis intersecting the overhanging portion of the platform for directing coolant from the plenum onto the back side of the overhanging portion.
a plenum located on the back side of the platform; and at least one impingement hole extending through a wall of the plenum and having an axis intersecting the overhanging portion of the platform for directing coolant from the plenum onto the back side of the overhanging portion.
9. The turbine vane as defined in claim 8, wherein said at least one impingement hole has an axis intersecting the platform.
10. The turbine vane as defined in claim 9, wherein said axis is slanted relative to said platform.
11. The turbine vane as defined in claim 8, wherein said plenum is defined in a root portion depending from the back side of the platform.
12. The turbine vane as defined in claim 11, wherein the wall in which is defined said at least one impingement hole includes a rear mounting flange forming part of the root portion.
13. The turbine vane as defined in claim 8, wherein said platform prevents coolant to flow from the plenum to the gas path side of the platform.
14. A turbine section for a gas turbine engine, comprising a turbine nozzle adapted to direct a stream of hot combustion gases to a turbine rotor, the turbine rotor having a plurality of circumferentially distributed blades projecting radially outwardly from a rotor disk, the rotor disk having a front rotor disk cavity, the turbine nozzle comprising a plurality of vanes extending radially between inner and outer bands forming radially inner and outer boundaries for the stream of hot combustion gases, each of a plurality of said vanes having a plenum located radially inwardly of said inner band, and at least one impingement hole oriented to cause coolant in the plenum to impinge onto a radially inwardly facing surface of the inner band and then flow into the front rotor disk cavity intermediate the turbine nozzle and the turbine rotor to at least partly purge the cavity from the hot combustion gases.
15. The turbine section as defined in claim 14, wherein said at least one impingement hole is defined in a rear mounting flange depending radially inwardly from the inner band.
16. The turbine section as defined in claim 14, wherein said inner band prevents coolant to flow from the plenum to a radially outwardly facing surface of the platform.
17. A method of cooling an overhanging portion of a platform of a turbine vane, comprising the steps of: a) feeding cooling air into a plenum located underneath the platform and b) causing at least part of the cooling air in the plenum to impinge onto an undersurface of the overhanging portion of the platform.
18. The method as defined in claim 17, comprising the step of defining at least one impingement hole in a rear mounting flange depending from the undersurface of the platform, the impingement hole being in communication with the plenum and having an exit located below the platform.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/008,978 US7452184B2 (en) | 2004-12-13 | 2004-12-13 | Airfoil platform impingement cooling |
US11/008,978 | 2004-12-13 |
Publications (2)
Publication Number | Publication Date |
---|---|
CA2528049A1 true CA2528049A1 (en) | 2006-06-13 |
CA2528049C CA2528049C (en) | 2011-12-06 |
Family
ID=36584096
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CA2528049A Expired - Fee Related CA2528049C (en) | 2004-12-13 | 2005-11-28 | Airfoil platform impingement cooling |
Country Status (2)
Country | Link |
---|---|
US (1) | US7452184B2 (en) |
CA (1) | CA2528049C (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2093381A1 (en) * | 2008-02-25 | 2009-08-26 | Siemens Aktiengesellschaft | Turbine blade or vane with cooled platform |
Families Citing this family (25)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20090169361A1 (en) * | 2007-12-29 | 2009-07-02 | Michael Scott Cole | Cooled turbine nozzle segment |
US20090165275A1 (en) * | 2007-12-29 | 2009-07-02 | Michael Scott Cole | Method for repairing a cooled turbine nozzle segment |
US8296945B2 (en) * | 2007-12-29 | 2012-10-30 | General Electric Company | Method for repairing a turbine nozzle segment |
US8206101B2 (en) * | 2008-06-16 | 2012-06-26 | General Electric Company | Windward cooled turbine nozzle |
US8246297B2 (en) * | 2008-07-21 | 2012-08-21 | Pratt & Whitney Canada Corp. | Shroud segment cooling configuration |
EP2211024A1 (en) * | 2009-01-23 | 2010-07-28 | Siemens Aktiengesellschaft | A gas turbine engine |
US8113784B2 (en) * | 2009-03-20 | 2012-02-14 | Hamilton Sundstrand Corporation | Coolable airfoil attachment section |
US8292573B2 (en) * | 2009-04-21 | 2012-10-23 | General Electric Company | Flange cooled turbine nozzle |
US8356975B2 (en) * | 2010-03-23 | 2013-01-22 | United Technologies Corporation | Gas turbine engine with non-axisymmetric surface contoured vane platform |
US9976433B2 (en) | 2010-04-02 | 2018-05-22 | United Technologies Corporation | Gas turbine engine with non-axisymmetric surface contoured rotor blade platform |
US8529194B2 (en) * | 2010-05-19 | 2013-09-10 | General Electric Company | Shank cavity and cooling hole |
US8702374B2 (en) * | 2011-01-28 | 2014-04-22 | Siemens Aktiengesellschaft | Gas turbine engine |
US8840370B2 (en) | 2011-11-04 | 2014-09-23 | General Electric Company | Bucket assembly for turbine system |
WO2015130425A2 (en) * | 2014-02-03 | 2015-09-03 | United Technologies Corporation | Gas turbine engine cooling fluid composite tube |
US9752447B2 (en) * | 2014-04-04 | 2017-09-05 | United Technologies Corporation | Angled rail holes |
WO2016028310A1 (en) | 2014-08-22 | 2016-02-25 | Siemens Aktiengesellschaft | Shroud cooling system for shrouds adjacent to airfoils within gas turbine engines |
US9982560B2 (en) * | 2015-01-16 | 2018-05-29 | United Technologies Corporation | Cooling feed orifices |
JP6546481B2 (en) * | 2015-08-31 | 2019-07-17 | 川崎重工業株式会社 | Exhaust diffuser |
EP3141702A1 (en) * | 2015-09-14 | 2017-03-15 | Siemens Aktiengesellschaft | Gas turbine guide vane segment and method of manufacturing |
US10066488B2 (en) | 2015-12-01 | 2018-09-04 | General Electric Company | Turbomachine blade with generally radial cooling conduit to wheel space |
US10247009B2 (en) | 2016-05-24 | 2019-04-02 | General Electric Company | Cooling passage for gas turbine system rotor blade |
DE102016217320A1 (en) * | 2016-09-12 | 2018-03-15 | Siemens Aktiengesellschaft | Gas turbine with separate cooling for turbine and exhaust housing |
US10895167B2 (en) * | 2017-05-30 | 2021-01-19 | Raytheon Technologies Corporation | Metering hole geometry for cooling holes in gas turbine engine |
US10526917B2 (en) * | 2018-01-31 | 2020-01-07 | United Technologies Corporation | Platform lip impingement features |
CN112081632A (en) * | 2020-10-16 | 2020-12-15 | 北京全四维动力科技有限公司 | Turbine stator blade of gas turbine and gas turbine adopting same |
Family Cites Families (18)
Publication number | Priority date | Publication date | Assignee | Title |
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GB1350471A (en) * | 1971-05-06 | 1974-04-18 | Secr Defence | Gas turbine engine |
US4348157A (en) * | 1978-10-26 | 1982-09-07 | Rolls-Royce Limited | Air cooled turbine for a gas turbine engine |
US4302148A (en) * | 1979-01-02 | 1981-11-24 | Rolls-Royce Limited | Gas turbine engine having a cooled turbine |
GB2064016B (en) * | 1979-11-22 | 1983-03-16 | Rolls Royce | Variable position seal for a turbine disc |
US4375891A (en) * | 1980-05-10 | 1983-03-08 | Rolls-Royce Limited | Seal between a turbine rotor of a gas turbine engine and associated static structure of the engine |
FR2519374B1 (en) * | 1982-01-07 | 1986-01-24 | Snecma | DEVICE FOR COOLING THE HEELS OF MOBILE BLADES OF A TURBINE |
US5197852A (en) * | 1990-05-31 | 1993-03-30 | General Electric Company | Nozzle band overhang cooling |
GB9204417D0 (en) * | 1992-02-29 | 1992-04-15 | Lucas Ind Plc | Fuel pumping apparatus |
US5252026A (en) * | 1993-01-12 | 1993-10-12 | General Electric Company | Gas turbine engine nozzle |
GB9305012D0 (en) * | 1993-03-11 | 1993-04-28 | Rolls Royce Plc | Sealing structures for gas turbine engines |
JPH10259703A (en) * | 1997-03-18 | 1998-09-29 | Mitsubishi Heavy Ind Ltd | Shroud for gas turbine and platform seal system |
JP3337393B2 (en) * | 1997-04-23 | 2002-10-21 | 三菱重工業株式会社 | Gas turbine cooling blade |
EP0902164B1 (en) * | 1997-09-15 | 2003-04-02 | ALSTOM (Switzerland) Ltd | Cooling of the shroud in a gas turbine |
DE19756734A1 (en) * | 1997-12-19 | 1999-06-24 | Bmw Rolls Royce Gmbh | Passive gap system of a gas turbine |
US6077035A (en) * | 1998-03-27 | 2000-06-20 | Pratt & Whitney Canada Corp. | Deflector for controlling entry of cooling air leakage into the gaspath of a gas turbine engine |
US6341939B1 (en) * | 2000-07-31 | 2002-01-29 | General Electric Company | Tandem cooling turbine blade |
US6416284B1 (en) * | 2000-11-03 | 2002-07-09 | General Electric Company | Turbine blade for gas turbine engine and method of cooling same |
GB2402442B (en) * | 2003-06-04 | 2006-05-31 | Rolls Royce Plc | Cooled nozzled guide vane or turbine rotor blade platform |
-
2004
- 2004-12-13 US US11/008,978 patent/US7452184B2/en active Active
-
2005
- 2005-11-28 CA CA2528049A patent/CA2528049C/en not_active Expired - Fee Related
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2093381A1 (en) * | 2008-02-25 | 2009-08-26 | Siemens Aktiengesellschaft | Turbine blade or vane with cooled platform |
WO2009106464A1 (en) * | 2008-02-25 | 2009-09-03 | Siemens Aktiengesellschaft | Turbine blade or vane with cooled platform |
Also Published As
Publication number | Publication date |
---|---|
CA2528049C (en) | 2011-12-06 |
US7452184B2 (en) | 2008-11-18 |
US20060127212A1 (en) | 2006-06-15 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
EEER | Examination request | ||
MKLA | Lapsed |
Effective date: 20210831 |
|
MKLA | Lapsed |
Effective date: 20191128 |